CMC BOAS arrangement

Abstract

A blade outer air seal includes a base portion. A first wall and a second wall extend from the base portion. The first wall is circumferentially spaced from the second wall. The first and second walls extend at an angle less than 90° from the base portion. The first and second walls extend towards one another.

The invention claimed is: 
     
       1. A blade outer air seal, comprising:
 a base portion; 
 a first wall and a second wall extending from the base portion, the first wall circumferentially spaced from the second wall, the first and second walls extend in an axial direction along at least 80% of an axial length of the base portion, the first and second walls extending at an angle less than 90° from the base portion, the first and second walls extending towards one another, and wherein the first and second walls provide angled surfaces configured to receive a carrier therebetween. 
 
     
     
       2. The blade outer air seal of  claim 1 , wherein a first hook extends outward from the first wall and a second hook extends outward from the second wall. 
     
     
       3. The blade outer air seal of  claim 2 , wherein the first and second hooks are substantially parallel to the base portion. 
     
     
       4. The blade outer air seal of  claim 3 , wherein the first and second hooks extend away from one another. 
     
     
       5. The blade outer air seal of  claim 2 , wherein the first and second hooks extend away from one another. 
     
     
       6. The blade outer air seal of  claim 2 , wherein the base portion, the first and second walls, and the first and second hooks have the same thickness. 
     
     
       7. The blade outer air seal of  claim 1 , wherein the first and second walls are configured to engage with a wedge seal. 
     
     
       8. The blade outer air seal of  claim 1 , wherein the base portion is configured to be adjacent the carrier. 
     
     
       9. The blade outer air seal of  claim 1 , wherein a tab extends axially forward from the first and second walls. 
     
     
       10. The blade outer air seal of  claim 1 , wherein a surface extends from the base portion axially aft of the first and second walls. 
     
     
       11. The blade outer air seal of  claim 1 , wherein the blade outer air seal is a ceramic matrix composite material. 
     
     
       12. The blade outer air seal of  claim 1 , wherein the angle is between 20° and 70°. 
     
     
       13. The blade outer air seal of  claim 1 , wherein the angled surfaces are configured to engage a first surface and a second surface of the carrier, the first surface and the second surface form an inward dovetail shape. 
     
     
       14. The blade outer air seal of  claim 1 , wherein the first wall and first hook are configured to abut a second wall and a second hook of an adjacent blade outer air seal to form a cavity. 
     
     
       15. The blade outer air seal of  claim 1 , wherein the base portion extends between a first circumferential side and a second circumferential side, the first wall arranged at the first circumferential side and the second wall arranged at the second circumferential side. 
     
     
       16. A turbine section for a gas turbine engine, comprising:
 a turbine blade extending radially outwardly to a radially outer tip and for rotation about an axis of rotation; 
 a blade outer air seal having a plurality of seal segments arranged circumferentially about an axis and mounted radially outward of the radially outer tip by a carrier; 
 at least one of the seal segments having a base portion, a first wall and a second wall extending from the base portion, the first wall circumferentially spaced from the second wall, the first and second walls extend in an axial direction along at least 80% of an axial length of the base portion, the first and second walls extending at an angle less than 90° from the base portion, the first and second walls extending towards one another, and wherein the first and second walls provide angled surfaces configured to receive a portion of the carrier therebetween. 
 
     
     
       17. The turbine section of  claim 16 , wherein the first wall and a first hook of the at least one seal segment are arranged adjacent a second wall and a second hook of an adjacent seal segment to form a seal cavity therebetween. 
     
     
       18. The turbine section of  claim 16 , wherein a first hook extends outward from the first wall and a second hook extends outward from the second wall, the first and second hooks extend away from one another. 
     
     
       19. The turbine section of  claim 18 , wherein the first and second hooks are substantially parallel to the base portion. 
     
     
       20. The turbine section of  claim 16 , wherein the base portion extends between a first circumferential side and a second circumferential side, the first wall arranged at the first circumferential side and the second wall arranged at the second circumferential side.